Classifications

• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C19/00—Alloys based on nickel or cobalt
  • C22C19/03—Alloys based on nickel or cobalt based on nickel
  • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
  • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
  • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
  • B23K35/24—Selection of soldering or welding materials proper
  • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
  • B23K35/3033—Ni as the principal constituent
  • B23K35/304—Ni as the principal constituent with Cr as the next major constituent
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C19/00—Alloys based on nickel or cobalt
  • C22C19/03—Alloys based on nickel or cobalt based on nickel
  • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
  • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
  • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C19/00—Alloys based on nickel or cobalt
  • C22C19/03—Alloys based on nickel or cobalt based on nickel
  • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
  • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
  • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
  • F01D5/288—Protective coatings for blades
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/22—Fuel supply systems
  • F02C7/232—Fuel valves; Draining valves or systems

Definitions

• the present invention relates to a nickel-base ⁇ / ⁇ ′ superalloy with multiple reactive elements and use of the superalloy in complex materials.
• Nickel-base ⁇ / ⁇ ′ superalloys are essential for critical components in aero and land based gas turbines, but are used also in other applications.
• the difference between said superalloys depend on the level of knowledge and production technology available at the time they were developed, and, on different relative emphasis on properties such as cost, oxidation resistance, corrosion resistance, strengthening, alloy stability, ductility, weldability and compatibility with other alloys in complex material systems.
• Nickel-base ⁇ / ⁇ ′ superalloys are used in single crystal, directionally solidified or equiaxed form.
• a y matrix which is essentially Ni with elements like Co, Cr, Mo, W and Re in solid solution
• ⁇ ′ particles which are essentially Ni3Al with elements like Ta, Ti, Nb and V in solid solution.
• Grain boundaries if present, are usually decorated by carbides and/or borides which provide cohesive strength.
• Zr also contributes to grain boundary cohesion.
• Grain boundaries in directionally solidified components are usually protected by significant additions of Hf.
• Zr and Hf can also contribute to the reactive element effect for improved cyclic oxidation resistance. Reactive element effects can also be obtained from Si and rare earths.
• Elements like Mo, W and Re provide solution strengthening of the y matrix, and, Ta, Ti, Nb and V provide solution strengthening of the ⁇ ′ particles.
• Al provides strengthening as it increases the amount of ⁇ ′ particles, and increases the concentration of Mo, W and Re in the ⁇ matrix.
• Nickel-base ⁇ / ⁇ ′ superalloys can seldom be regarded as low cost, but, if the levels of expensive elements such as W and Ta are kept moderate, and the levels of very expensive elements such as Re, Ru and noble metals like Pt are kept very low or are excluded, the cost can be regarded as moderate in context.
• Corrosion resistance is provided by Cr. Less than 12 wt % Cr is regarded as poor, at least 12 wt % Cr as moderate, at least 16 wt % Cr as good, and at least 20 wt % Cr as excellent.
• High strength base alloys typically use in the order of 4 to 10 wt % Mo+W+Re for matrix strengthening, and in the order of 4-10 wt % Ti+Ta+Nb for strengthening of the ⁇ ′ particles, and contain between 40 and 70 vol % ⁇ ′ particles.
• IN738LC contains about 43 vol % particles, 4.4 wt % Mo+W and 6.2 wt % Ti+Ta+Nb.
• low strength alloys such as Haynes-214, which is still equivalent in strength to traditional weld filler alloys such as IN625, contain no strengthening of the matrix or the particles, and the ⁇ ′ particle content is small or zero at high service temperatures.
• a moderate strengthening level is taken to be a ⁇ ′ content in the 30-50 vol % range and in the range of 2 to 8 wt % of the sum of matrix and particle strengthening elements.
• phase precipitation is a reduction in creep strength, and phase stability has therefore been an important subject for base alloy design.
• extensive phase precipitation may cause loss of ductility, said phases are often known as brittle phases. It should be noted that stability may be even more important for alloys in complex materials systems due to the interdiffusion which might locally increase the concentration of alloy additions as described above.
• Classical coating alloys tend to be based on ⁇ and ⁇ / ⁇ phase structures which provide high Al reservoirs.
• the ⁇ phase is essentially NiAl.
• the problem with these alloys is that their brittleness implies that they are normally only used as a thin layer. Therefore, they are sensitive to interdiffusion with the base alloy, e.g. through loss of Al due to diffusion to low Al base alloys and/or reduction of oxidation resistance due to interdiffusion of Ti from the base alloy into the coating.
• strengthening elements have been added to these classical coatings alloys to retard the interdiffusion rates, typically using Re, Ru and Ta additions. [Subramanian] teaches that the Re additions in SiCoat2464 significantly increases the oxidation resistance thanks to a reduced rate of Al interdiffusion.
• an alloy may be used in a material system which includes an aluminide, it is important for the alloy to be compatible with said aluminide.
• a hot component such as a gas turbine first stage vane made in a [low Al high Ti] alloy like IN939.
• a common problem is local overheating on the platforms, and classical coating systems tend to provide a quite limited life due to interdiffusion with the [low Al high Ti] substrate.
• the ability to increase the thickness from standard levels to, say, 2 mm in the locally hot area, i.e. to apply cladding, would significantly increase the component life.
• Application of e.g. a PtAl coating on top could then be used to further increase this component life.
• the full creep strength of the substrate is not necessary, but, some creep strength is still useful to resist erosion and rumpling of the surface due to the high velocity hot gas stream, because increased surface roughness implies higher heat transfer into the component, and thus an accelerated oxidation process.
• IN939 has a composition, in wt %, given by Ni-19Co-22Cr-2W-2A1-3.7Ti-1.4Ta-1Nb-0.1Zr-0.15C-0.01B.
• That of IN738LC is Ni-8.5Co-16Cr-1.8Mo-2.6W-3.4Al-3.4Ti-1.8Ta-0.9Nb-0.09Zr-0.08C-0.01B.
• That of IN792 is Ni-9Co-12.5Cr-1.8Mo-4.2W-3.4A1-4.2Ti-4.2Ta-0.08C-0.015B.
• Mo is partly replaced by W for improved corrosion resistance
• Al is partly replaced by Ti, Nb and Ta for improved creep strength through increased strengthening of the ⁇ ′ particles.
• these alloys contain high Ti levels.
• alloys such as Mar M-247 which has a composition, in wt %, given by Ni-10Co-8Cr-0.7Mo-10W-5.65Al-1Ti-3Ta-1.5Hf-0.15C.
• the introduction of directional solidification led to derivative alloys such as CM247DS, and single crystal casting led to derivative alloys such as Rene N5 and CMSX-4 which have compositions, in wt %, given by Ni-7.5Co-7Cr-1.5Mo-5W-3Re-6.1Al-6.5Ta-0.1Hf-0.05C and Ni-9Co-6.5Cr-0.6Mo-6.5W-3Re-5.65Al-1Ti-6.5Ta-0.1Hf respectively.
• Haynes-214 has a basic composition in wt % given by Ni-3Fe-16Cr-4.5Al and also contains small levels of Zr, Si and Y to provide reactive element effects. It combines good corrosion resistance, excellent oxidation resistance and high weldability. The creep strength is comparatively poor because it contains no strengthening elements.
• Patent application EP 1914327A1 discloses an alloy with at least 12 wt % Cr, at least 4 wt % Al, at least 7.5 wt % Ta and at least 3 wt % of the sum of matrix strengthening elements Mo+W+Re. This implies that it is a high strength alloy, and, consequently we cannot assume good weldability in the sense described above.
• Patent application WO 2009109521 discloses an alloy with between 17 and 21 wt % Cr, between 4.0 and 4.7 wt % Al, and moderate levels of matrix and particle strengthening elements. This is likely to have most of the properties of the present invention, but even a moderate loss of Al would reduce an oxidation resistance which otherwise might have been excellent.
• a typical embodiment is STAL18 with a composition, in wt %, Ni-5Co-18Cr-0.8Mo-2.5W-4.4Al-4.4Ta-0.03C-0.03Zr-0.005B-0.1Hf-0.1Si-0.02Ce
• ⁇ / ⁇ ′′ based coatings is SV-20 with a nominal composition, in wt %, of Ni-25Cr-2.7Si-5.5A1-0.5Y-1Ta. Because of the high Cr content and the relatively high ⁇ ′ content caused by these Al and Si levels, the ⁇ / ⁇ ′ structure is not stable.
• Patent EP1426759 teaches that SV-20 has an equilibrium content of ⁇ 20 vol % ⁇ -Cr below 900° C., and that thermal cycling between room temperature and temperatures above 900° C. will result in solutioning, re-precipitation, and some levels of non-equilibrium products.
• the objective with the present invention is to provide a nickel-base ⁇ / ⁇ ′′ superalloy with a unique blend of moderate cost, excellent oxidation resistance, good corrosion resistance, moderate strength, good stability, good ductility, good weldability, good compatibility with aluminide coatings, and a margin against moderate loss of Al in complex material systems.
• a further objective is its use in hot components such as, but not restricted to, blades, vanes, heat shields, sealings and combustor parts in gas turbines.
• a further objective is its use as filler alloy for repair welding and/or cladding of such hot components.
• a further objective is its use as protective coating and/or as bond coat in a TBC system on such hot components.
• a further objective is its dual use as coating and/or bond coat, and, for repair and/or cladding on such hot components.
• a further objective is its use as intermediate layer between the base alloy and another coating and/or bond coat on such hot components.
• a further objective is its use in polycrystalline, directionally solidified or single crystal form in such components.
• a further objective is its production by processes such as, but not restricted to, precision casting, laser welding/cladding, hot box welding, laser sintering, cold spraying, explosion welding and vacuum plasma spraying.
• a further objective is its production by low S processing.
• a further objective is its use as part of material systems as exemplified above produced by low S processing.
• the alloy disclosed in this invention does not have the strength necessary for its use as base alloy in highly loaded areas of hot components, as needed to e.g. avoid excessive elongation of gas turbine blades, its strength is sufficient for many hot components, and, for large areas of most hot components, e.g. on platforms and blade tips.
• the alloy is therefore useful for e.g. manufacturing of many hot components and cladding or repair of most hot components, thanks to the range of other properties described above.
• the composition of this invention is based on the following idea: Good corrosion resistance and stability require at most a moderate level of ⁇ ′ particles and at most moderate levels of strengthening elements to allow for a high Cr content without extensive brittle phase precipitation. This also implies good ductility and weldability. At the same time, excellent oxidation resistance require formation of a continuous and very adherent Al2O3 scale, and this must be achieved despite the restriction on the ⁇ ′ content, and therefore on the Al content, and the fact that there must be at least some strengthening of the ⁇ ′ particles which also adds to the ⁇ ′ content.
• the solution is to rely on Ta which is beneficial for the oxidation resistance rather than the deleterious elements Ti, Nb or V for strengthening of the ⁇ ′ particles, and, to utilize clean production methodology and multiple reactive elements, to make up for a comparatively moderate Al level.
• Cobalt levels up to 20 wt % are generally utilized in nickel-base ⁇ / ⁇ ′ superalloys, and it seems reasonable to allow for the same variation to e.g. allow for embodiments matched against different base alloys. Fe additions are less common, but moderate Fe additions are used in e.g. the highly oxidation resistant alloy Haynes-214.
• Moderate strengthening of the matrix elements is provided by between 0.5 and 3 wt of Mo+W, with a limit to at most 2 wt % Mo to preserve the good hot corrosion resistance provided by the high Cr content.
• the oxidation resistance is based on 4.8 to 6 wt % Al.
• Haynes-214 shows that 4.5 wt % can be sufficient for excellent cyclic oxidation resistance when supported by high levels of Cr and an appropriate multiple reactive element recipe.
• the lower Al limit is set a bit above the 4.5 wt % used in Haynes-214 to provide some margin against interdiffusion effects when the alloy is used in material systems as described above. More than 6 wt % Al is not compatible with the Cr levels needed for good hot corrosion resistance given the requirement on adequate phase stability.
• Moderate strengthening of the ⁇ ′ particles is provided by between 1.5 and 5 wt % Ta.
• C+B levels of up to 0.2 wt % are commonly used for grain boundary strengthening, and even when the alloy is used in single crystal form it is advantageous to include at least 0.01 wt % for low angle boundary tolerance.
• the Zr content should be at least 0.01 wt % to contribute to multiple reactive element doping, and can be up to 0.2 wt % to e.g. contribute to grain boundary strengthening.
• the Hf content should be at least 0.05 wt % to contribute to multiple reactive element doping, and can be up to 1.5 wt % to contribute to e.g. rumpling resistance of an applied aluminide coating, or, for grain boundary strengthening when the alloy is used in directionally solidified form.
• the Si content should be at least 0.05 wt % to contribute to multiple reactive element doping, but can be up to 1.0 wt % to e.g. improve the corrosion resistance.
• a limit on 1 wt % is set to avoid unstable alloy behavior.
• the sum of rare earths should be at least 0.01 wt % to provide an appropriate level of retained rare earths after the production process when said production process has a high degree of rare earth retention.
• the sum of rare earths may have to be up to 0.5 wt % to provide an appropriate level of retained rare earths after the production process when said production process has a low degree of rare earth retention.
• compositions disclosed here relates to the stage in the production chain prior to the actual application, which could be e.g. casting of a component from bar stock, vacuum plasma spraying from powder, or laser welding from powder, except in the case of cold spraying and similar non-melting processes in which it relates to the stage before the last melting prior to said cold spraying or a similar process.
• the alloy may include up to 20 wt % of Co+Fe, between 17 and 21 wt % Cr, between 0.5 and 3 wt % of Mo+W, at most 2 wt % Mo, between 4.8 and 6 wt % Al, between 1.5 and 5 wt % Ta, between 0.01 and 0.2 wt % of C+B, between 0.01 and 0.2 wt % Zr, between 0.05 and 1.5 wt % Hf, between 0.05 and 1.0 wt % Si, and between 0.01 and 0.5 wt % of the sum of rare earths such that at least two rare earths are present, and at most 0.3 wt % of any rare earth is present.
• the alloy may include up to 20 wt % of Co+Fe, between 17 and 21 wt % Cr, between 0.5 and 3 wt % of Mo+W, at most 2 wt % Mo, between 4.8 and 6 wt % Al, between 1.5 and 5 wt % Ta, between 0.01 and 0.2 wt % of C+B, between 0.01 and 0.2 wt % Zr, between 0.05 and 1.5 wt % Hf, between 0.05 and 1.0 wt % Si, and between 0.01 and 0.5 wt % of the sum of rare earths such that at least two rare earths are present, and at most 0.3 wt % of any rare earth is present, and Y present only as an unavoidable impurity.
• the alloy may include between 2 and 8 wt % Co, between 17 and 19 wt % Cr, between 1 and 2.2 wt % W, between 4.8 and 5.8 wt % Al, between 2 and 4.5 wt % Ta, between 0.01 and 0.1 wt % of C+B, between 0.02 and 0.08 wt % Zr, between 0.1 and 0.5 wt % Hf, between 0.05 and 0.4 wt % Si, and between 0.02 and 0.2 wt % of the sum of rare earths of which at least two are present.
• the alloy may include between 4.5 and 5.5 wt % Co, between 18.2 and 19 wt % Cr, between 1.4 and 1.8 wt % W, between 5.2 and 5.5 wt % Al, between 2.8 and 3.6 wt % Ta, between 0.015 and 0.025 wt % C, between 0.04 and 0.07 wt % Zr, between 0.25 and 0.4 wt % Hf, between 0.07 and 0.13 wt % Si, and between 0.05 and 0.15 wt % (La+Y), at least 0.02 La, at least 0.02 Y.
• the alloy may include about 5.0 wt % Co, about 18.5 wt % Cr, about 1.6 wt % W, about 5.3 wt % Al, about 3.2 wt % Ta, about 0.02 wt % C, about 0.05 wt % Zr, about 0.3 wt % Hf, about 0.1 wt % Si, about 0.05 wt % Y and about 0.05 wt % La.
• the alloy may include between 2 and 8 wt % Co, between 17 and 19 wt % Cr, between 1 and 2.2 wt % W, between 4.8 and 5.8 wt % Al, between 2 and 4.5 wt % Ta, between 0.01 and 0.1 wt % of C+B, between 0.02 and 0.08 wt % Zr, between 0.1 and 0.5 wt % Hf, between 0.05 and 0.4 wt % Si, and between 0.05 and 0.5 wt % of the sum of rare earths, at most 0.3 of any rare earth, and Y present only as unavoidable impurity.
• the alloy may include between 4.5 and 5.5 wt % Co, between 18.2 and 19 wt % Cr, between 1.4 and 1.8 wt % W, between 5.2 and 5.5 wt % Al, between 2.8 and 3.6 wt % Ta, between 0.015 and 0.025 wt % C, between 0.04 and 0.07 wt % Zr, between 0.25 and 0.4 wt % Hf, between 0.07 and 0.13 wt % Si, and between 0.05 and 0.5 wt % of the sum of Ce+Gd, at least 0.02 wt % Ce, at least 0.02 wt % Gd, and at most 0.3 wt % of Gd or Ce.
• the alloy may include about 5 wt % Co, about 18.5 wt % Cr, about 1.6 wt % W, about 5.3 wt % Al, about 3.2 wt % Ta, about 0.02 wt % C, about 0.05 wt % Zr, about 0.3 wt % Hf, about 0.1 wt % Si, about 0.05 wt % Ce and about 0.05 wt % Gd.
• the alloy may include between 2 and 8 wt % Co, between 17 and 19 wt % Cr, between 0.5 and 1.5 wt % Mo, between 4.8 and 5.8 wt % Al, between 2 and 4.5 wt % Ta, between 0.01 and 0.1 wt % of C+B, between 0.02 and 0.08 wt % Zr, between 0.1 and 0.5 wt % Hf, between 0.05 and 0.4 wt % Si, and between 0.02 and 0.2 wt % of the sum of rare earths of which at least two are present in the alloy.
• the alloy may include, measured in wt %, between 4.5 and 5.5 wt % Co, between 18.2 and 19 wt % Cr, between 0.8 and 1.2 wt % Mo, between 5.2 and 5.5 wt % Al, between 2.8 and 3.6 wt % Ta, between 0.015 and 0.025 wt % C, between 0.04 and 0.07 wt % Zr, between 0.25 and 0.4 wt % Hf, between 0.07 and 0.13 wt % Si, and between 0.05 and 0.15 wt % (La+Y), at least 0.02 wt % La, at least 0.02 wt % Y.
• the alloy may include about 5.3 wt % Co, about 18.5 wt % Cr, about 1.0 wt % Mo, about 5.3 wt % Al, about 3.2 wt % Ta, about 0.02 wt % C, about 0.05 wt % Zr, about 0.3 wt % Hf, about 0.1 wt % Si, about 0.05 wt % Y and about 0.05 wt % La.
• the ally may include between 2 and 8 wt % Co, between 17 and 19 wt % Cr, between 0.5 and 1.5 wt % Mo, between 4.8 and 5.8 wt % Al, between 2 and 4.5 wt % Ta, between 0.01 and 0.1 wt % of C+B, between 0.02 and 0.08 wt % Zr, between 0.1 and 0.5 wt % Hf, between 0.05 and 0.4 wt % Si, and between 0.02 and 0.5 wt % of the sum of rare earths of which at least two are present in the alloy, at most 0.3 wt % of any rare earth, and Y present only as an unavoidable impurity.
• the alloy may include, measured in wt %, between 4.8 and 5.8 wt % Co, between 18.2 and 19 wt % Cr, between 0.8 and 1.2 wt % Mo, between 5.2 and 5.5 wt % Al, between 2.8 and 3.6 wt % Ta, between 0.015 and 0.025 wt % C, between 0.04 and 0.07 wt % Zr, between 0.25 and 0.4 wt % Hf, between 0.07 and 0.13 wt % Si, and between 0.05 and 0.5 wt % (Ce+Gd), at least 0.02 wt % Ce, at least 0.02 wt % Gd, at most 0.3 wt % Ce or Gd.
• Ce+Gd 0.05 and 0.5 wt %
• the alloy may include about 5.3 wt % Co, about 18.5 wt % Cr, about 1.0 wt % Mo, about 5.3 wt % Al, about 3.2 wt % Ta, about 0.02 wt % C, about 0.05 wt % Zr, about 0.3 wt % Hf, about 0.1 wt % Si, about 0.05 wt % Ce and about 0.05 wt % Gd.
• the alloy may include, measured in wt %, between 2 and 8 wt % Co, between 20 and 21 wt % Cr, between 0.5 and 1.5 wt % W, between 4.7 and 5.3 wt % Al, between 1.5 and 2.5 wt % Ta, between 0.01 and 0.1 wt % of C+B, between 0.02 and 0.08 wt % Zr, between 0.1 and 0.5 wt % Hf, between 0.1 and 0.7 wt % Si, and between 0.02 and 0.2 wt % of the sum of rare earths of which at least two are present in the alloy.
• the alloy may include, measured in wt %, between 4.5 and 5.5 wt % Co, between 20.2 and 21.8 wt % Cr, between 0.8 and 1.2 wt % W, between 4.8 and 5.2 wt % Al, between 1.8 and 2.2 wt % Ta, between 0.015 and 0.025 wt % C, between 0.04 and 0.07 wt % Zr, between 0.25 and 0.4 wt % Hf, between 0.3 and 0.5 wt % Si, and between 0.05 and 0.15 wt % (La+Y), at least 0.02 wt % La, at least 0.02 wt % Y.
• the alloy may include about 5 wt % Co, about 20.5 wt % Cr, about 1 wt % W, about 5 wt % Al, about 2 wt % Ta, about 0.02 wt % C, about 0.05 wt % Zr, about 0.3 wt % Hf, about 0.4 wt % Si, about 0.05 wt % Y and about 0.05 wt % La.
• the alloy may include between 2 and 8 wt % Co, between 20 and 21 wt % Cr, between 0.5 and 1.5 wt % W, between 4.7 and 5.3 wt % Al, between 1.5 and 2.5 wt % Ta, between 0.01 and 0.1 wt % of C+B, between 0.02 and 0.08 wt % Zr, between 0.1 and 0.5 wt % Hf, between 0.1 and 0.7 wt % Si, between 0.02 and 0.5 wt % of the sum of rare earths such that at least two rare earths are present in the alloy, Y present only as an unavoidable impurity, at most 0.3 wt % of any rare earth.
• the alloy may include, measured in wt %, between 4.5 and 5.5 wt % Co, between 20.2 and 20.8 wt % Cr, between 0.8 and 1.2 wt % W, between 4.8 and 5.2 wt % Al, between 1.8 and 2.2 wt % Ta, between 0.015 and 0.025 wt % C, between 0.04 and 0.07 wt % Zr, between 0.25 and 0.4 wt % Hf, between 0.3 and 0.5 wt % Si, and between 0.05 and 0.5 wt % (Ce+Gd), at least 0.02 wt % Ce, and at least 0.02 wt % Gd, at most 0.3 wt % Ce or Gd.
• the alloy may include about 5 wt % Co, about 20.5 wt % Cr, about 1 wt % W, about 5 wt % Al, about 2 wt % Ta, about 0.02 wt % C, about 0.05 wt % Zr, about 0.3 wt % Hf, about 0.4 wt % Si, about 0.05 wt % Ce and about 0.05 wt % Gd.
• the superalloy according to the invention should be processed with a clean production process to produce an alloy with at most 10 ppmw S, preferably less than 2 ppmw S. Additionally, each part of a complex material system in which the superalloys according to the invention is included should be processed with a clean production process which results in at most 10 ppmw S, preferably less than 2 ppmw S.
• Mo will e.g. reduce the solvus temperature whereas W increases it, and while the difference in may only be a few degree Celsius, this might enable or prevent a heat treatment aimed at one of the alloys within a complex material system.
• the choice of reactive elements may need to be adjusted to the reactive elements used in other alloys in a complex material system. Consequently, more than one embodiment is needed, and further embodiments can be designed to optimize compatibility with e.g. specific base alloys or for specific corrosive environments.
• alloys having at least two wt % of the sum of matrix strengthening elements like Mo, W and Re, and, particle strengthening elements like Ti, Ta, Nb and V, alloys such as Haynes 214 are excluded.
• alloys with good alloy stability alloys such as SV-20 are excluded.
• Patent application WO 2009109521 is in many ways similar to the present invention. The difference is that it has less Al than in the invention, and therefore less margin against loss of Al in a complex material system before it starts to loose it's initially good to excellent oxidation resistance.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Mechanical Engineering (AREA)
• Materials Engineering (AREA)
• Metallurgy (AREA)
• Organic Chemistry (AREA)
• General Engineering & Computer Science (AREA)
• Combustion & Propulsion (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Applications Claiming Priority (3)

Publications (1)

Family

ID=40793022

Family Applications (1)

Country Status (5)

Cited By (7)

Families Citing this family (11)

Citations (4)

Family Cites Families (8)

• 2009
  • 2009-04-27 EP EP09005851A patent/EP2248923A1/en not_active Withdrawn
• 2010
  • 2010-04-07 US US13/266,276 patent/US20120189488A1/en not_active Abandoned
  • 2010-04-07 RU RU2011148124/02A patent/RU2500827C2/ru not_active IP Right Cessation
  • 2010-04-07 WO PCT/EP2010/054593 patent/WO2010124923A1/en not_active Ceased
  • 2010-04-07 CN CN201080018553.XA patent/CN102414331B/zh not_active Expired - Fee Related
  • 2010-04-07 EP EP10713904A patent/EP2425029A1/en not_active Withdrawn

Patent Citations (4)

Also Published As

Similar Documents

Legal Events